US20190242614A1 - Airfoil blade and method of assembly - Google Patents
Airfoil blade and method of assembly Download PDFInfo
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- US20190242614A1 US20190242614A1 US16/234,931 US201816234931A US2019242614A1 US 20190242614 A1 US20190242614 A1 US 20190242614A1 US 201816234931 A US201816234931 A US 201816234931A US 2019242614 A1 US2019242614 A1 US 2019242614A1
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- Prior art keywords
- shell
- airfoil shell
- airfoil
- legs
- pair
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F24—HEATING; RANGES; VENTILATING
- F24F—AIR-CONDITIONING; AIR-HUMIDIFICATION; VENTILATION; USE OF AIR CURRENTS FOR SCREENING
- F24F13/00—Details common to, or for air-conditioning, air-humidification, ventilation or use of air currents for screening
- F24F13/08—Air-flow control members, e.g. louvres, grilles, flaps or guide plates
- F24F13/10—Air-flow control members, e.g. louvres, grilles, flaps or guide plates movable, e.g. dampers
- F24F13/14—Air-flow control members, e.g. louvres, grilles, flaps or guide plates movable, e.g. dampers built up of tilting members, e.g. louvre
- F24F13/1406—Air-flow control members, e.g. louvres, grilles, flaps or guide plates movable, e.g. dampers built up of tilting members, e.g. louvre characterised by sealing means
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F24—HEATING; RANGES; VENTILATING
- F24F—AIR-CONDITIONING; AIR-HUMIDIFICATION; VENTILATION; USE OF AIR CURRENTS FOR SCREENING
- F24F13/00—Details common to, or for air-conditioning, air-humidification, ventilation or use of air currents for screening
- F24F13/08—Air-flow control members, e.g. louvres, grilles, flaps or guide plates
- F24F13/10—Air-flow control members, e.g. louvres, grilles, flaps or guide plates movable, e.g. dampers
- F24F13/14—Air-flow control members, e.g. louvres, grilles, flaps or guide plates movable, e.g. dampers built up of tilting members, e.g. louvre
- F24F13/15—Air-flow control members, e.g. louvres, grilles, flaps or guide plates movable, e.g. dampers built up of tilting members, e.g. louvre with parallel simultaneously tiltable lamellae
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F24—HEATING; RANGES; VENTILATING
- F24F—AIR-CONDITIONING; AIR-HUMIDIFICATION; VENTILATION; USE OF AIR CURRENTS FOR SCREENING
- F24F13/00—Details common to, or for air-conditioning, air-humidification, ventilation or use of air currents for screening
- F24F13/08—Air-flow control members, e.g. louvres, grilles, flaps or guide plates
- F24F13/10—Air-flow control members, e.g. louvres, grilles, flaps or guide plates movable, e.g. dampers
- F24F13/14—Air-flow control members, e.g. louvres, grilles, flaps or guide plates movable, e.g. dampers built up of tilting members, e.g. louvre
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F24—HEATING; RANGES; VENTILATING
- F24F—AIR-CONDITIONING; AIR-HUMIDIFICATION; VENTILATION; USE OF AIR CURRENTS FOR SCREENING
- F24F13/00—Details common to, or for air-conditioning, air-humidification, ventilation or use of air currents for screening
- F24F13/08—Air-flow control members, e.g. louvres, grilles, flaps or guide plates
- F24F13/10—Air-flow control members, e.g. louvres, grilles, flaps or guide plates movable, e.g. dampers
- F24F13/14—Air-flow control members, e.g. louvres, grilles, flaps or guide plates movable, e.g. dampers built up of tilting members, e.g. louvre
- F24F13/1426—Air-flow control members, e.g. louvres, grilles, flaps or guide plates movable, e.g. dampers built up of tilting members, e.g. louvre characterised by actuating means
Definitions
- the present invention relates to dampers and, more particularly, to an airfoil blade for a damper and a method of assembling an airfoil blade.
- Dampers have long been used in a variety of fluid handling applications to control the flow of various types of fluids.
- Typical uses of industrial dampers include the handling of process control fluids, the handling of fluids in power plants, and the handling of high speed fan discharge streams.
- Industrial dampers are usually subjected to relatively high pressures and must have considerable strength in order to be capable of withstanding the forces that are applied to them.
- the damper construction normally includes a rigid frame which defines a flow passage controlled by a plurality of damper blades that each pivot between open and closed positions about a respective axle.
- the blades are often interconnected by a linkage which moves all of them in unison to control the fluid flow rate in accordance with the damper blade position.
- flat damper blades are often used, it has long been recognized that airfoil shapes can be used to enhance the fluid flow. Airfoil blades are thickest in the center at the pivot axis and taper toward each edge to present an aerodynamically efficient shape which minimizes turbulence and other undesirable effects such as noise generation and stresses on the flow passage and other components of the fluid handling system.
- damper blades have been formed by bending multiple sheets of steel and joining them together to form an airfoil shape.
- a bead of silicone or other sealant may be manually deposited at the respective ends of each blade to provide for an air tight seal between the damper blades when in a closed position.
- a bracket is mounted to each end of the blade, which is necessary to locate and accommodate an axle on which each blade pivots.
- an airfoil blade assembly includes a first shell member having a body having a first lock seam formed at one end thereof and a free distal end opposite the first lock seam, and a second shell member having a body having and a second lock seam formed at one end thereof and an a free distal end opposite the second lock seam.
- the second shell member is inverted with respect to the first shell member. The free distal end of the first shell member is captured within the second lock seam of the second shell member and the free distal end of the second shell member is captured within the first lock seam of the first shell member to lock the blades to one another.
- a method of assembling an airfoil blade includes roll forming first and second shell members of the airfoil blade on a roll forming machine and depositing a sealant bead in an end seam of each of the shell members on the roll forming machine in an inline process.
- the method also includes joining two shell members to one another and crimping respective ends of each shell member to form a lock seam which captures a free edge of the opposed shell member therein to lock the shell members to one another.
- a damper assembly includes a frame, an axle rotatably mounted to the frame, and an airfoil blade assembly operatively mounted to the axle.
- the airfoil blade assembly includes an upper shell member and a lower shell member, wherein said lower shell member is invertedly disposed and connected to said upper shell member.
- FIG. 1 is a schematic illustration of a flow control damper equipped with airfoil blades in a fully open position.
- FIG. 2 is a cross-sectional view of an airfoil blade constructed according to an embodiment of the present invention.
- FIG. 3 is cross-sectional view of a shell member of the airfoil blade of FIG. 2 .
- FIG. 4 is an enlarged, detail view of area A of FIG. 3 .
- FIG. 5 is a cross-sectional view of the shell member of FIG. 3 after a roll forming operation.
- FIG. 6 is a cross-sectional view of the shell member of FIG. 3 , illustrating the insertion of a silicone bead in an end seam of the shell member.
- FIG. 7 is a cross-sectional view of the shell member of FIG. 3 after the end seam is closed.
- FIG. 8 is a cross-sectional view of the shell member of FIG. 3 after the shell member has been cut to length and locating apertures are punched in the shell member.
- FIG. 9 is a cross-sectional view of the airfoil blade of FIG. 2 , illustrating the joining of two shell members to one another.
- reference numeral 10 generally designates an airfoil blade constructed in accordance with the present invention.
- the airfoil blade is formed from a pair of relatively thin shell members 12 , 14 which themselves may be formed from galvanized steel sheets. Each of the sheets is initially flat, and the sheets are bent into the shapes shown by suitable roll forming techniques.
- the shell members 12 , 14 are substantially identical and are manufactured in the same manner.
- the upper shell member 12 essentially mirrors the lower shell member 14 , to which it is interconnected in the manner discussed hereinafter.
- Each shell member 12 , 14 includes an end seam 16 at one end thereof which is bent back upon the body of the respective shell member 12 , 14 to provide a lock seam 18 which captures the free side edge 20 of the opposed shell member 12 , 14 .
- the two shell members 12 , 14 are rigidly interlocked along both of their side edges 20 .
- the edges of the blade 10 are parallel.
- the airfoil blade 10 has a hollow airfoil shape best shown in FIG. 2 .
- the shell members 12 , 14 form the walls of the blade 10 , and the shell members 12 , 14 converge toward the interlocked edges to give the blade 10 a tapered profile.
- Center portions 22 of the respective upper and lower shell member 12 , 14 are spaced apart from one another to provide the center portion of the blade 10 with a predetermined thickness.
- the blade 10 gradually tapers from the center portion toward each of the opposite edges.
- Shell member 14 is substantially identical to shell member 12 and is manufactured in a substantially identical manner, however only shell member 12 is being shown for clarity.
- shell member 12 may be formed from a sheet of galvanized steel in a roll forming operation.
- the shell member 12 includes a first edge having a generally V-shaped end seam 16 and an opposed free edge 20 .
- the shell member 12 is generally arcuate in shape and has a center portion 22 . On opposing sides of the center portion 22 , downwardly depending legs are formed by bending the sheet of material back upon itself.
- a first depending leg or seam 24 is formed between the end seam 16 and the center portion 22 and a second depending leg or seam 26 is formed between the center portion and the free edge 20 .
- the height of the first depending leg 24 is greater than the height of the second depending leg 26 .
- the shell member 12 also includes a pair of spaced apart strengthening ribs 28 formed in the body of the shell member 12 adjacent to the center portion 22 and outside the legs 24 , 26 , respectively.
- the ribs 28 are formed by corrugations in the shell member 12 and serve as stiffeners which enhance the strength of the airfoil blade 10 .
- Each rib 28 has a V-shaped configuration and extends into the interior of the blade 10 .
- the legs 24 and 26 of each shell 12 / 14 of the airfoil blade assembly 10 are preferably formed to be unequal in length so as to avoid any undesirable and damaging material deformation that can occur to the metal blank should the roll forming process that forms the airfoil blade assembly 10 be required to form both legs, 24 and 26 , to each be as long as the first depending leg 24 .
- legs 24 and 26 be of differing lengths, the assembly process is streamlined, whereby installers in the field can easily arrange the two halves/ shells 12 / 14 of the airfoil blade assembly 10 in their proper orientation merely by ensuring that the shorter of the two legs, leg 26 , is always located on the outside of each of the legs 24 (as best seen in FIG. 2 ).
- legs 24 and 26 are of uneven lengths the present invention ensures against material deformation, as well as providing a visual and structural guide for the final assembly of the airfoil blade 10 .
- leg 24 and 26 are such that, when shell 12 and shell 14 are mated to one another, each of the shorter legs 26 provides a significant strengthening and stiffening capability to the longer legs 24 .
- the present invention provides the structurally robust, axially-aligned center portion 22 , as shown best in FIG. 2 .
- leg 24 and 26 are generally formed to be unequal in length, preferably formed such that the shorter leg 26 is substantially half the length of the longer leg 24 , and more preferably that leg 24 is at least one third the length of leg 24 .
- the strengthening legs 24 and 26 of the present invention provide structural support for the airfoil blade assembly 10 as a whole, but by virtue of the nature of their construction, the legs 24 and 26 also provide a robust anchor point for any axial control rod disposed therein and used to move the airfoil blade assembly 10 between open and closed positions.
- the structure of the center portion 22 of the airfoil blade assembly 10 is such that, as opposed to known axial control rods that extend the entire axial length of known airfoil blade assemblies, the current invention permits the use of shortened axial control rods which need only to be captured within the control portions 22 formed on distal ends of the assembled airfoil blade assembly 10 .
- robust nature of the center portion 22 flowing from the structure and orientation of the legs 24 and 26 , promotes efficiency and reduces manufacturing costs by allowing shortened axial control rods to be used adjacent each distal end of the airfoil blade assembly 10 instead of longer, heavier and more expensive continuous rods running the axial length of the airfoil blade assembly, as is commonly known in the art.
- the end seam 16 is generally V-shaped and has a first leg portion 30 that extends from the shell member body at a substantially ninety-degree angle, a second leg portion 32 that extends from the first leg portion 30 to form an angle, ⁇ , therebetween, and an arcuate tail portion 34 that extends from the second leg portion 32 over the open end of the end seam 16 .
- the angle, ⁇ is between approximately 10 and 20 degrees and, more preferably, is approximately 15 degrees.
- shell member 12 and the end seam 16 , strengthening ribs 28 , depending legs 24 , 26 and center portion 22 thereof, are formed by repetitively bending, or roll forming, the sheet material on a single roll forming machine.
- a bead of sealant 36 such as silicone or vinyl, is then disposed along the length of the shell member 12 within the end seam 16 .
- the sealant 36 is deposited in the end seam 16 as part of an in-line manufacturing process on the same roll forming machine on which the shell member 12 is formed. The same roll forming machine is then utilized to close the end seam 16 , as illustrated in FIG. 7 .
- the bead of sealant 36 includes a tail 37 , captured within the seam 16 , further assisting in locating and fixing the bead of sealant 36 along the lateral edge of the airfoil blade assembly 10 .
- seam 16 further includes an inwardly deformed locking tab 39 , further arresting the sealant bead 36 from undesirable movement or dislocation.
- the bead of embedded sealant 36 is not positioned or intended to prevent the entrance of moisture of contaminants into the body of the airfoil blade assembly 10 itself. Instead, the sealant bead 36 of the present invention is left exposed to run continuously along the lateral edge of, for example, each of the airfoil blade assemblies 10 shown in FIG. 1 .
- the sealant bead 36 disposed along each lateral edge of each of the airfoil blade assemblies 10 will become trapped between adjacent airfoil blade assemblies, thereby providing an elastic and resilient sealing member between such adjacent blade assemblies.
- the shell member 12 is then cut to a desired length, and apertures 38 are pierced in shell member 12 in the center portion 22 at cutoff, as shown in FIG. 8 .
- the apertures 38 are located approximately 1.25 inches from the leading and trailing edges of each shell member 12 (i.e., from the left and right edges of a completed shell member).
- the formation of the shell members 12 , deposition of the sealant in the end seam 16 , closing of the end seam 16 , piercing of the apertures 38 and cutting the shell members 12 to the desired length is accomplished on a single machine without necessitating intervention or manipulation by an operator or technician.
- the shell members 12 , 14 are cut to a length of between approximately 8 inches and 60 inches, although the shell members 12 , 14 may be cut to any length to form a blade assembly 10 having any desired span.
- shell members 12 Once multiple shell members 12 are produced, an operator will collect the shell members 12 .
- One shell member is then flipped over on its backside (e.g., shell member 14 in FIG. 9 ).
- a mating shell member 12 is then placed directly on top of shell member 14 , as shown in FIG. 9 .
- a pin fixture 100 having pins 102 may then be placed on each end such that pins 102 extend through the apertures 38 in both shell members 12 , 14 to properly locate and align the shell members, 12 , 14 with one another.
- the airfoil blade 10 is then transferred to a bending/ joining apparatus where the end seams 16 of each shell member 12 , 14 are bent towards the center portion 22 (to close the ninety-degree bend between the shell member body and the first leg portion 30 of the end seam 16 ). This bending operation forms lock seams 18 which capture the free edges 20 of the opposed shell member 12 , 14 therein.
- the completed airfoil blade assembly 10 is illustrated in FIG. 2 .
- the sealant beads 36 are located on opposed edges (front and back), and opposed sides (upper and lower) of the blade assembly 10 .
- the sealant beads 36 may be formed from silicone where the intended use for the damper blades 10 is in fire dampers.
- the sealant bead may be formed from other materials, such as vinyl and the like, without departing from the broader aspects of the present invention.
- each shell member 12 , 14 define a longitudinal passageway or channel 40 for the passage of an axle, as hereinafter described.
- the longer, first depending legs 24 extend from the shell member body from which they are formed substantially to the blade body of the opposed shell member.
- the shorter, second depending leg 26 of each shell member is configured to lie outside the first depending leg 24 of the opposing shell member, and functions to provide bolstering support for the first depending legs 24 , as illustrated in FIG. 2 (i.e., the second legs 26 buttress the first legs 26 ).
- the bolstering legs 26 help to maintain the structural rigidity of the first depending legs 24 , thereby maintaining the integrity and square form of the channel 40 during operation.
- the four standing seams i.e., the first and second depending legs 24 , 26 of each shell member 12 , 14 ) provide strength to the completed blade assembly 10 and provide a pocket for the axle, as discussed hereinafter. Accordingly, there is no need to utilize a separate bracket to locate the axle, which eliminates many of the tedious steps required for existing methods of assembly.
- the airfoil blade assemblies 10 may be dropped, one by one, into a rigid damper frame 200 having opposite sides 202 , a top portion 204 , and a bottom portion 206 .
- the frame 200 is normally installed in a fluid flow passage, a portion of which is formed by a damper opening 216 presented within the frame 200 between the sides and the top and bottom of the frame.
- the axle 208 for each blade may then be slid through the frame 200 and through the channel 40 within each blade assembly 10 .
- the axle may have a cross-section that is substantially similar to the square cross-section of the channel 40 , at least along the longitudinal extent where the axle is received within the channel 40 .
- the axles 208 may be approximately 1 ⁇ 2′′ in thickness and have a square cross-section.
- the axles 208 are supported for pivotal movement on the opposite sides 202 of the frame 200 .
- the axles 208 may be supported by round bushings that are themselves fixed in the frame 200 .
- the axle channel 40 formed in the blade assembly 10 keeps the blades from twisting on the axles under torque.
- Each axle 208 may be rigidly connected to a crank arm 210 , and all of the crank arms 210 may be connected by a vertical linkage 212 pivoted at 214 to the crank arms 210 .
- This arrangement pivots the blade assemblies 10 in unison between the fully opened positioned shown in FIG. 1 and the fully closed position in which the blades 10 are oriented vertically to close the damper opening.
- Other means of linking the axles 208 so that the blades 10 may be opened or closed in unison may also be utilized without departing from the broader aspects of the present invention.
- the damper blades 10 can be positioned anywhere between the fully opened and fully closed positions.
- the sheet members 12 and 14 can be relatively light gauge sheet metal so that both the cost and the weight of the damper are reduced without sacrificing strength or other desirable performance characteristics. For example, acceptable results can be obtained from the use of 20 gauge coil stock, although other sheet thicknesses may also be utilized.
- the configuration of the center portion 22 of the present invention permits the use of two separate and non-continuous axle control rods, each captured with the distally located control portions 22 of the airfoil blade assembly 10 , thus reducing the material cost, weight and complexity of the airfoil blade assembly 10 of the present invention.
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Abstract
Description
- The present application is Continuation-in-Part of U.S. utility patent application Ser. No. 15/ 000,678 filed on Jan. 19, 2016, which itself claims priority to U.S. provisional application Ser. No. 62/ 106,868, filed on Jan. 23, 2015, each of which are hereby incorporated by reference in their entirety.
- The present invention relates to dampers and, more particularly, to an airfoil blade for a damper and a method of assembling an airfoil blade.
- Dampers have long been used in a variety of fluid handling applications to control the flow of various types of fluids. Typical uses of industrial dampers include the handling of process control fluids, the handling of fluids in power plants, and the handling of high speed fan discharge streams. Industrial dampers are usually subjected to relatively high pressures and must have considerable strength in order to be capable of withstanding the forces that are applied to them.
- The damper construction normally includes a rigid frame which defines a flow passage controlled by a plurality of damper blades that each pivot between open and closed positions about a respective axle. The blades are often interconnected by a linkage which moves all of them in unison to control the fluid flow rate in accordance with the damper blade position. Although flat damper blades are often used, it has long been recognized that airfoil shapes can be used to enhance the fluid flow. Airfoil blades are thickest in the center at the pivot axis and taper toward each edge to present an aerodynamically efficient shape which minimizes turbulence and other undesirable effects such as noise generation and stresses on the flow passage and other components of the fluid handling system.
- In the past, damper blades have been formed by bending multiple sheets of steel and joining them together to form an airfoil shape. Typically, in a separate step, a bead of silicone or other sealant may be manually deposited at the respective ends of each blade to provide for an air tight seal between the damper blades when in a closed position. In a further separate step, a bracket is mounted to each end of the blade, which is necessary to locate and accommodate an axle on which each blade pivots. As will be readily appreciated, however, existing airfoil blades are very time consuming and tedious to manufacture, requiring numerous and separate manual steps. In addition, existing blades often require additional strengthening ribs to bolster the blade under high speed flow, which may further increase the cost and labor involved.
- Accordingly, it is desirable to provide an airfoil blade assembly that is easier, more cost effective, and less labor-intensive to produce than existing blades.
- According to the present invention, an airfoil blade assembly includes a first shell member having a body having a first lock seam formed at one end thereof and a free distal end opposite the first lock seam, and a second shell member having a body having and a second lock seam formed at one end thereof and an a free distal end opposite the second lock seam. The second shell member is inverted with respect to the first shell member. The free distal end of the first shell member is captured within the second lock seam of the second shell member and the free distal end of the second shell member is captured within the first lock seam of the first shell member to lock the blades to one another.
- According to another embodiment of the present invention a method of assembling an airfoil blade includes roll forming first and second shell members of the airfoil blade on a roll forming machine and depositing a sealant bead in an end seam of each of the shell members on the roll forming machine in an inline process. The method also includes joining two shell members to one another and crimping respective ends of each shell member to form a lock seam which captures a free edge of the opposed shell member therein to lock the shell members to one another.
- According to yet another embodiment of the present invention, a damper assembly is provided. The damper assembly includes a frame, an axle rotatably mounted to the frame, and an airfoil blade assembly operatively mounted to the axle. The airfoil blade assembly includes an upper shell member and a lower shell member, wherein said lower shell member is invertedly disposed and connected to said upper shell member.
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FIG. 1 is a schematic illustration of a flow control damper equipped with airfoil blades in a fully open position. -
FIG. 2 is a cross-sectional view of an airfoil blade constructed according to an embodiment of the present invention. -
FIG. 3 is cross-sectional view of a shell member of the airfoil blade ofFIG. 2 . -
FIG. 4 is an enlarged, detail view of area A ofFIG. 3 . -
FIG. 5 is a cross-sectional view of the shell member ofFIG. 3 after a roll forming operation. -
FIG. 6 is a cross-sectional view of the shell member ofFIG. 3 , illustrating the insertion of a silicone bead in an end seam of the shell member. -
FIG. 7 is a cross-sectional view of the shell member ofFIG. 3 after the end seam is closed. -
FIG. 8 is a cross-sectional view of the shell member ofFIG. 3 after the shell member has been cut to length and locating apertures are punched in the shell member. -
FIG. 9 is a cross-sectional view of the airfoil blade ofFIG. 2 , illustrating the joining of two shell members to one another. - With reference to the drawings,
reference numeral 10 generally designates an airfoil blade constructed in accordance with the present invention. With particular reference toFIG. 2 , the airfoil blade is formed from a pair of relativelythin shell members FIG. 2 , theshell members upper shell member 12 essentially mirrors thelower shell member 14, to which it is interconnected in the manner discussed hereinafter. - Each
shell member end seam 16 at one end thereof which is bent back upon the body of therespective shell member lock seam 18 which captures thefree side edge 20 of theopposed shell member free side edges 20, the twoshell members side edges 20. The edges of theblade 10 are parallel. - The
airfoil blade 10 has a hollow airfoil shape best shown inFIG. 2 . Theshell members blade 10, and theshell members Center portions 22 of the respective upper andlower shell member blade 10 with a predetermined thickness. Theblade 10 gradually tapers from the center portion toward each of the opposite edges. - Turning now to
FIG. 3 , a cross-sectional view ofshell member 12 is illustrated. Shellmember 14 is substantially identical toshell member 12 and is manufactured in a substantially identical manner, however onlyshell member 12 is being shown for clarity. As discussed above,shell member 12 may be formed from a sheet of galvanized steel in a roll forming operation. - The
shell member 12 includes a first edge having a generally V-shaped end seam 16 and an opposedfree edge 20. Theshell member 12 is generally arcuate in shape and has acenter portion 22. On opposing sides of thecenter portion 22, downwardly depending legs are formed by bending the sheet of material back upon itself. In particular, a first depending leg orseam 24 is formed between theend seam 16 and thecenter portion 22 and a second depending leg orseam 26 is formed between the center portion and thefree edge 20. As shown, the height of the first dependingleg 24 is greater than the height of the second dependingleg 26. Theshell member 12 also includes a pair of spaced apart strengtheningribs 28 formed in the body of theshell member 12 adjacent to thecenter portion 22 and outside thelegs ribs 28 are formed by corrugations in theshell member 12 and serve as stiffeners which enhance the strength of theairfoil blade 10. Eachrib 28 has a V-shaped configuration and extends into the interior of theblade 10. - As therefore shown in
FIGS. 2 and 3 in total, thelegs shell 12/ 14 of theairfoil blade assembly 10 are preferably formed to be unequal in length so as to avoid any undesirable and damaging material deformation that can occur to the metal blank should the roll forming process that forms theairfoil blade assembly 10 be required to form both legs, 24 and 26, to each be as long as the first dependingleg 24. - Moreover, by having
legs shells 12/ 14 of theairfoil blade assembly 10 in their proper orientation merely by ensuring that the shorter of the two legs,leg 26, is always located on the outside of each of the legs 24 (as best seen inFIG. 2 ). - It will therefore be readily appreciated that by forming
legs airfoil blade 10. - It will also be readily appreciated that the arrangement of
legs shell 12 andshell 14 are mated to one another, each of theshorter legs 26 provides a significant strengthening and stiffening capability to thelonger legs 24. In just this fashion, the present invention provides the structurally robust, axially-alignedcenter portion 22, as shown best inFIG. 2 . In this regard, it is envisioned thatleg shorter leg 26 is substantially half the length of thelonger leg 24, and more preferably thatleg 24 is at least one third the length ofleg 24. - Known airfoil blade assemblies typically require the addition of one of more separate structures within the airfoil blade assembly to support an axial control rod disposed for movement of the airfoil blade assembly. In contrast, the present invention has recognized that by forming the structurally robust and axially-aligned
center portion 22 via the nesting oflegs inner legs 24/ 26 to also provide the housing for any axial control rod disposed therein, without the use of any additional structure to the interior of theairfoil blade assembly 10. - Indeed, as will be appreciated by one of ordinary skill, not only do the strengthening
legs airfoil blade assembly 10 as a whole, but by virtue of the nature of their construction, thelegs airfoil blade assembly 10 between open and closed positions. - Still further, the structure of the
center portion 22 of theairfoil blade assembly 10 is such that, as opposed to known axial control rods that extend the entire axial length of known airfoil blade assemblies, the current invention permits the use of shortened axial control rods which need only to be captured within thecontrol portions 22 formed on distal ends of the assembledairfoil blade assembly 10. Thus, robust nature of thecenter portion 22, flowing from the structure and orientation of thelegs airfoil blade assembly 10 instead of longer, heavier and more expensive continuous rods running the axial length of the airfoil blade assembly, as is commonly known in the art. - As shown in
FIGS. 3 and 4 , theend seam 16 is generally V-shaped and has afirst leg portion 30 that extends from the shell member body at a substantially ninety-degree angle, asecond leg portion 32 that extends from thefirst leg portion 30 to form an angle, α, therebetween, and an arcuate tail portion 34 that extends from thesecond leg portion 32 over the open end of theend seam 16. In an embodiment, the angle, α, is between approximately 10 and 20 degrees and, more preferably, is approximately 15 degrees. - With reference to
FIGS. 5-10 assembly of theairfoil blade 10 utilizingshell members FIG. 5 ,shell member 12, and theend seam 16, strengtheningribs 28, dependinglegs center portion 22 thereof, are formed by repetitively bending, or roll forming, the sheet material on a single roll forming machine. - As the
shell member 12 is suitably formed to the desired shape, and concurrent to the ongoing roll forming process, a bead ofsealant 36, such as silicone or vinyl, is then disposed along the length of theshell member 12 within theend seam 16. Importantly, thesealant 36 is deposited in theend seam 16 as part of an in-line manufacturing process on the same roll forming machine on which theshell member 12 is formed. The same roll forming machine is then utilized to close theend seam 16, as illustrated inFIG. 7 . - As also shown in
FIGS. 5-10 , the bead ofsealant 36 includes atail 37, captured within theseam 16, further assisting in locating and fixing the bead ofsealant 36 along the lateral edge of theairfoil blade assembly 10. Indeed, as perhaps best seen inFIG. 2 ,seam 16 further includes an inwardlydeformed locking tab 39, further arresting thesealant bead 36 from undesirable movement or dislocation. - As will be readily appreciated by a review of
FIGS. 2 and 5-10 , the bead of embeddedsealant 36 is not positioned or intended to prevent the entrance of moisture of contaminants into the body of theairfoil blade assembly 10 itself. Instead, thesealant bead 36 of the present invention is left exposed to run continuously along the lateral edge of, for example, each of theairfoil blade assemblies 10 shown inFIG. 1 . As will therefore be readily appreciated, when the individualairfoil blade assemblies 10 are moved to their ‘closed’ position (they are shown in their ‘open’ position inFIG. 1 ), the lateral edge of their respective planar faces will come into contact with the lateral edge of each adjacent airfoil blade assemblies. Thus, as will be appreciated, thesealant bead 36 disposed along each lateral edge of each of theairfoil blade assemblies 10 will become trapped between adjacent airfoil blade assemblies, thereby providing an elastic and resilient sealing member between such adjacent blade assemblies. - In stark contrast, known airfoil blade systems mechanically attach sealing members to the airfoil blade assemblies after the roll forming process is concluded, thus increasing the complexity, cost and manufacturing time of the resultant airfoil blade assembly. It is therefore an important aspect of the present invention that not only is the
sealant bead 36 applied during the roll forming process, but it is done such that a portion/ tail of the sealant bead is captured within a sealing seam already formed adjacent each lateral edge of theairfoil blade assembly 10, thereby saving manufacturing costs and time. - The
shell member 12 is then cut to a desired length, andapertures 38 are pierced inshell member 12 in thecenter portion 22 at cutoff, as shown inFIG. 8 . In an embodiment, theapertures 38 are located approximately 1.25 inches from the leading and trailing edges of each shell member 12 (i.e., from the left and right edges of a completed shell member). Importantly, the formation of theshell members 12, deposition of the sealant in theend seam 16, closing of theend seam 16, piercing of theapertures 38 and cutting theshell members 12 to the desired length is accomplished on a single machine without necessitating intervention or manipulation by an operator or technician. In an embodiment, theshell members shell members blade assembly 10 having any desired span. - Once
multiple shell members 12 are produced, an operator will collect theshell members 12. One shell member is then flipped over on its backside (e.g.,shell member 14 inFIG. 9 ). Amating shell member 12 is then placed directly on top ofshell member 14, as shown inFIG. 9 . Apin fixture 100 havingpins 102 may then be placed on each end such that pins 102 extend through theapertures 38 in bothshell members airfoil blade 10 is then transferred to a bending/ joining apparatus where the end seams 16 of eachshell member first leg portion 30 of the end seam 16). This bending operation forms lockseams 18 which capture thefree edges 20 of theopposed shell member - This formation of the lock seams 18, and capturing the
free edges 20 of thecorresponding shell member shell members airfoil blade assembly 10. Thepin fixtures 100 may then be removed and reused in the assembly of another airfoil blade. The completedairfoil blade assembly 10 is illustrated inFIG. 2 . As shown, thesealant beads 36 are located on opposed edges (front and back), and opposed sides (upper and lower) of theblade assembly 10. In an embodiment, thesealant beads 36 may be formed from silicone where the intended use for thedamper blades 10 is in fire dampers. In other embodiments, the sealant bead may be formed from other materials, such as vinyl and the like, without departing from the broader aspects of the present invention. - Importantly, as best illustrated in
FIG. 2 , the opposed dependinglegs shell member channel 40 for the passage of an axle, as hereinafter described. In particular, as shown inFIG. 2 , the longer, first dependinglegs 24 extend from the shell member body from which they are formed substantially to the blade body of the opposed shell member. The shorter, second dependingleg 26 of each shell member is configured to lie outside the first dependingleg 24 of the opposing shell member, and functions to provide bolstering support for the first dependinglegs 24, as illustrated inFIG. 2 (i.e., thesecond legs 26 buttress the first legs 26). In this manner, the bolsteringlegs 26 help to maintain the structural rigidity of the first dependinglegs 24, thereby maintaining the integrity and square form of thechannel 40 during operation. Moreover, the four standing seams (i.e., the first and second dependinglegs shell member 12, 14) provide strength to the completedblade assembly 10 and provide a pocket for the axle, as discussed hereinafter. Accordingly, there is no need to utilize a separate bracket to locate the axle, which eliminates many of the tedious steps required for existing methods of assembly. - Referring to
FIG. 1 , once theairfoil blade assemblies 10 are constructed in the manner hereinbefore described, they may be dropped, one by one, into arigid damper frame 200 havingopposite sides 202, atop portion 204, and abottom portion 206. Theframe 200 is normally installed in a fluid flow passage, a portion of which is formed by a damper opening 216 presented within theframe 200 between the sides and the top and bottom of the frame. - The
axle 208 for each blade may then be slid through theframe 200 and through thechannel 40 within eachblade assembly 10. In an embodiment, the axle may have a cross-section that is substantially similar to the square cross-section of thechannel 40, at least along the longitudinal extent where the axle is received within thechannel 40. In an embodiment, theaxles 208 may be approximately ½″ in thickness and have a square cross-section. Theaxles 208 are supported for pivotal movement on theopposite sides 202 of theframe 200. In particular, theaxles 208 may be supported by round bushings that are themselves fixed in theframe 200. As will be readily appreciated, theaxle channel 40 formed in theblade assembly 10 keeps the blades from twisting on the axles under torque. - Each
axle 208 may be rigidly connected to a crankarm 210, and all of thecrank arms 210 may be connected by avertical linkage 212 pivoted at 214 to the crankarms 210. This arrangement pivots theblade assemblies 10 in unison between the fully opened positioned shown inFIG. 1 and the fully closed position in which theblades 10 are oriented vertically to close the damper opening. Other means of linking theaxles 208 so that theblades 10 may be opened or closed in unison may also be utilized without departing from the broader aspects of the present invention. Thedamper blades 10 can be positioned anywhere between the fully opened and fully closed positions. - As discussed previously, and due to the provision and configuration of the depending
legs blade assembly 10 may be obviated. This eliminates costly and tedious manufacturing steps. The configuration of theselegs blade assembly 10 in comparison to existing blades. In addition, by roll forming the shell members and depositing thesealant bead 38 as part of an inline manufacturing process on a single machine, manufacturing efficiency and cost reductions may therefore be realized. - The enhanced stiffening of the center portion of the
blade 10 provided by thelegs ribs 28 eliminates the need to add separate reinforcement tubes or other reinforcement members. Because of the enhanced strength and resistance to deflection provided by thelegs ribs 28, thesheet members - Also, as an alternative to utilizing a
continuous axle 208 running from thecenter portion 22 adjacent one distal end of theairfoil blade assembly 10 to thecenter portion 22 adjacent the opposing distal end of theairfoil blade assembly 10, the configuration of thecenter portion 22 of the present invention permits the use of two separate and non-continuous axle control rods, each captured with the distally locatedcontrol portions 22 of theairfoil blade assembly 10, thus reducing the material cost, weight and complexity of theairfoil blade assembly 10 of the present invention. - Although this invention has been shown and described with respect to the detailed embodiments thereof, it will be understood by those of skill in the art that various changes may be made and equivalents may be substituted for elements thereof without departing from the scope of the invention. In addition, modifications may be made to adapt a particular situation or material to the teachings of the invention without departing from the essential scope thereof. Therefore, it is intended that the invention not be limited to the particular embodiments disclosed in the above detailed description, but that the invention will include all embodiments falling within the scope of this disclosure.
Claims (4)
Priority Applications (6)
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US16/234,931 US10955167B2 (en) | 2015-01-23 | 2018-12-28 | Airfoil blade and method of assembly |
MX2020007241A MX2020007241A (en) | 2018-12-28 | 2019-12-18 | Airfoil blade and method of assembly. |
PCT/US2019/067054 WO2020139648A1 (en) | 2018-12-28 | 2019-12-18 | Airfoil blade and method of assembly |
CA3093049A CA3093049C (en) | 2018-12-28 | 2019-12-18 | Airfoil blade and method of assembly |
US17/181,239 US11846443B2 (en) | 2015-01-23 | 2021-02-22 | Airfoil blade and method of assembly |
US18/388,430 US20240068704A1 (en) | 2015-01-23 | 2023-11-09 | Airfoil blade and method of assembly |
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US201562106868P | 2015-01-23 | 2015-01-23 | |
US15/000,678 US10208982B2 (en) | 2015-01-23 | 2016-01-19 | Airfoil blade and method of assembly |
US16/234,931 US10955167B2 (en) | 2015-01-23 | 2018-12-28 | Airfoil blade and method of assembly |
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US15/000,678 Continuation-In-Part US10208982B2 (en) | 2015-01-23 | 2016-01-19 | Airfoil blade and method of assembly |
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US17/181,239 Division US11846443B2 (en) | 2015-01-23 | 2021-02-22 | Airfoil blade and method of assembly |
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US20190242614A1 true US20190242614A1 (en) | 2019-08-08 |
US10955167B2 US10955167B2 (en) | 2021-03-23 |
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US16/234,931 Active US10955167B2 (en) | 2015-01-23 | 2018-12-28 | Airfoil blade and method of assembly |
US17/181,239 Active US11846443B2 (en) | 2015-01-23 | 2021-02-22 | Airfoil blade and method of assembly |
US18/388,430 Pending US20240068704A1 (en) | 2015-01-23 | 2023-11-09 | Airfoil blade and method of assembly |
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US17/181,239 Active US11846443B2 (en) | 2015-01-23 | 2021-02-22 | Airfoil blade and method of assembly |
US18/388,430 Pending US20240068704A1 (en) | 2015-01-23 | 2023-11-09 | Airfoil blade and method of assembly |
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Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20210190343A1 (en) * | 2019-12-18 | 2021-06-24 | The Gsi Group Llc | Ventilation shutter with louver having sealing lip |
US11655997B2 (en) * | 2019-12-20 | 2023-05-23 | Johnson Controls Tyco IP Holdings LLP | Damper blade assembly for HVAC system |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
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US3885347A (en) * | 1974-01-04 | 1975-05-27 | Borg Warner | Damper wind stop and blade seal design |
US3908529A (en) * | 1973-04-26 | 1975-09-30 | Francis J Mccabe | Backdraft damper |
US4382460A (en) * | 1981-11-23 | 1983-05-10 | Ben Tal Ram | Slats for assembly into door or window shutters |
Family Cites Families (3)
Publication number | Priority date | Publication date | Assignee | Title |
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US2643627A (en) | 1950-12-28 | 1953-06-30 | American Can Co | Method of producing cushion in seams of containers |
US4313609A (en) * | 1979-07-16 | 1982-02-02 | Clements Harold J | Sealing devices |
US10222089B2 (en) * | 2014-10-28 | 2019-03-05 | T.A. Morrison & Co. Inc. | Damper with integrated blade stop |
-
2018
- 2018-12-28 US US16/234,931 patent/US10955167B2/en active Active
-
2021
- 2021-02-22 US US17/181,239 patent/US11846443B2/en active Active
-
2023
- 2023-11-09 US US18/388,430 patent/US20240068704A1/en active Pending
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3908529A (en) * | 1973-04-26 | 1975-09-30 | Francis J Mccabe | Backdraft damper |
US3885347A (en) * | 1974-01-04 | 1975-05-27 | Borg Warner | Damper wind stop and blade seal design |
US4382460A (en) * | 1981-11-23 | 1983-05-10 | Ben Tal Ram | Slats for assembly into door or window shutters |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20210190343A1 (en) * | 2019-12-18 | 2021-06-24 | The Gsi Group Llc | Ventilation shutter with louver having sealing lip |
US11655997B2 (en) * | 2019-12-20 | 2023-05-23 | Johnson Controls Tyco IP Holdings LLP | Damper blade assembly for HVAC system |
Also Published As
Publication number | Publication date |
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US20210172647A1 (en) | 2021-06-10 |
US10955167B2 (en) | 2021-03-23 |
US20240068704A1 (en) | 2024-02-29 |
US11846443B2 (en) | 2023-12-19 |
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